A composite cooling structure inside a turbine moving blade

Abstract

The invention discloses a composite cooling structure inside a turbine moving blade, which comprises a leading edge swirl cooling channel, a middle chord U-shaped cooling channel and a trailing edge trapezoidal cooling channel. The U-shaped cooling channel includes an integrally formed U-shaped cooling channel inlet section, a U-shaped cooling channel outlet section, and a U-shaped cooling channel top turning area connecting the U-shaped cooling channel inlet section and the U-shaped cooling channel outlet section, U The inlet and outlet sections of the cooling channel and the swirl cooling channel are connected by a number of staggered jet holes; the entire surface of the cooling channel is arranged with a number of ball socket / ball convex, air film hole structures, U-shaped cooling channel and trailing edge trapezoidal cooling Several fin structures are arranged in the channel. The invention not only ensures the structural strength of the blade through the coupling of multiple structures, but also realizes the advantages of high heat transfer, low resistance, high adaptability and the like.

Description

technical field [0001] The invention belongs to the technical field of turbine cooling, and particularly relates to a composite cooling structure inside a turbine rotor blade. Background technique [0002] Gas turbine is a very important energy power equipment, which is widely used in energy, electric power, aerospace, aviation, ships, military and other fields. It is a strategically important equipment for national defense and energy power industry. The technological development level of jet engines and heavy-duty gas turbines is an important indicator to measure the strength of a country's manufacturing industry. Therefore, to carry out research on key technologies of gas turbines and develop gas turbines with independent intellectual property rights in my country will be important for my country's national economic development, energy security and national defense security. are of great significance. [0003] The improvement of gas turbine power and efficiency largely dep...

AI Technical Summary

Problems solved by technology

It is difficult to achieve the expected cooling effect by using a single cooling structure. Therefore, it is necessary to combine different cooling structures and give full play to the advantages of various cooling structures to further improve the enhanced heat transfer capacity of the internal cooling channel and adapt to the new generation of combustion gas. machine development

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